CN100579866C - Polyurethane lacquers as abrasion-resistant coatings - Google Patents
Polyurethane lacquers as abrasion-resistant coatings Download PDFInfo
- Publication number
- CN100579866C CN100579866C CN200680036844A CN200680036844A CN100579866C CN 100579866 C CN100579866 C CN 100579866C CN 200680036844 A CN200680036844 A CN 200680036844A CN 200680036844 A CN200680036844 A CN 200680036844A CN 100579866 C CN100579866 C CN 100579866C
- Authority
- CN
- China
- Prior art keywords
- filler
- particle diameter
- mohs
- hardness
- scale
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
- 239000004922 lacquer Substances 0.000 title claims abstract description 57
- 238000005299 abrasion Methods 0.000 title claims abstract description 56
- 239000004814 polyurethane Substances 0.000 title claims abstract description 56
- 229920002635 polyurethane Polymers 0.000 title claims abstract description 56
- 238000000576 coating method Methods 0.000 title claims abstract description 27
- 239000000945 filler Substances 0.000 claims abstract description 93
- 239000011159 matrix material Substances 0.000 claims abstract description 31
- 239000011248 coating agent Substances 0.000 claims abstract description 24
- 125000001931 aliphatic group Chemical group 0.000 claims abstract description 14
- 239000002245 particle Substances 0.000 claims description 45
- 239000003973 paint Substances 0.000 claims description 37
- 238000012856 packing Methods 0.000 claims description 21
- 239000000463 material Substances 0.000 claims description 14
- PNEYBMLMFCGWSK-UHFFFAOYSA-N Alumina Chemical compound [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 claims description 12
- 150000001875 compounds Chemical class 0.000 claims description 11
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 8
- MCMNRKCIXSYSNV-UHFFFAOYSA-N Zirconium dioxide Chemical compound O=[Zr]=O MCMNRKCIXSYSNV-UHFFFAOYSA-N 0.000 claims description 6
- 239000000919 ceramic Substances 0.000 claims description 6
- 229920003023 plastic Polymers 0.000 claims description 5
- 239000004033 plastic Substances 0.000 claims description 5
- 229910010271 silicon carbide Inorganic materials 0.000 claims description 4
- 235000012239 silicon dioxide Nutrition 0.000 claims description 4
- 239000000377 silicon dioxide Substances 0.000 claims description 4
- -1 akerite Chemical compound 0.000 claims description 3
- 229910052582 BN Inorganic materials 0.000 claims description 2
- PZNSFCLAULLKQX-UHFFFAOYSA-N Boron nitride Chemical compound N#B PZNSFCLAULLKQX-UHFFFAOYSA-N 0.000 claims description 2
- 239000000523 sample Substances 0.000 description 30
- 238000012360 testing method Methods 0.000 description 28
- 229910052751 metal Inorganic materials 0.000 description 26
- 239000002184 metal Substances 0.000 description 26
- 238000011160 research Methods 0.000 description 12
- 239000011256 inorganic filler Substances 0.000 description 8
- 229910003475 inorganic filler Inorganic materials 0.000 description 8
- 238000000034 method Methods 0.000 description 8
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 5
- 230000004087 circulation Effects 0.000 description 5
- 239000010936 titanium Substances 0.000 description 5
- 229910052719 titanium Inorganic materials 0.000 description 5
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 4
- 229910000831 Steel Inorganic materials 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 238000010926 purge Methods 0.000 description 4
- 239000010959 steel Substances 0.000 description 4
- 239000000654 additive Substances 0.000 description 3
- 230000000996 additive effect Effects 0.000 description 3
- 239000004411 aluminium Substances 0.000 description 3
- 229910052782 aluminium Inorganic materials 0.000 description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 3
- 238000004140 cleaning Methods 0.000 description 3
- 239000012530 fluid Substances 0.000 description 3
- 238000005498 polishing Methods 0.000 description 3
- 241001062009 Indigofera Species 0.000 description 2
- 206010023126 Jaundice Diseases 0.000 description 2
- 230000009471 action Effects 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000000835 fiber Substances 0.000 description 2
- 229910002804 graphite Inorganic materials 0.000 description 2
- 239000010439 graphite Substances 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 230000001771 impaired effect Effects 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 239000000049 pigment Substances 0.000 description 2
- 239000000843 powder Substances 0.000 description 2
- 239000000047 product Substances 0.000 description 2
- 230000008439 repair process Effects 0.000 description 2
- 238000005507 spraying Methods 0.000 description 2
- 230000000007 visual effect Effects 0.000 description 2
- 238000004260 weight control Methods 0.000 description 2
- 239000004593 Epoxy Substances 0.000 description 1
- 239000004952 Polyamide Substances 0.000 description 1
- 239000004698 Polyethylene Substances 0.000 description 1
- 229910004298 SiO 2 Inorganic materials 0.000 description 1
- 239000004699 Ultra-high molecular weight polyethylene Substances 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 230000032683 aging Effects 0.000 description 1
- 125000003118 aryl group Chemical group 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 239000006103 coloring component Substances 0.000 description 1
- 238000012505 colouration Methods 0.000 description 1
- 239000013065 commercial product Substances 0.000 description 1
- 230000003750 conditioning effect Effects 0.000 description 1
- 239000013530 defoamer Substances 0.000 description 1
- 238000000151 deposition Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000001066 destructive effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000003822 epoxy resin Substances 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 230000004927 fusion Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000011065 in-situ storage Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000000873 masking effect Effects 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 239000002105 nanoparticle Substances 0.000 description 1
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 description 1
- 239000003960 organic solvent Substances 0.000 description 1
- 238000010422 painting Methods 0.000 description 1
- 229920002647 polyamide Polymers 0.000 description 1
- 229920000647 polyepoxide Polymers 0.000 description 1
- 229920000573 polyethylene Polymers 0.000 description 1
- 238000012805 post-processing Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 239000003507 refrigerant Substances 0.000 description 1
- 238000007790 scraping Methods 0.000 description 1
- 239000000565 sealant Substances 0.000 description 1
- 239000002904 solvent Substances 0.000 description 1
- 230000035882 stress Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 1
- 229920000785 ultra high molecular weight polyethylene Polymers 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
- 238000009736 wetting Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/32—Air braking surfaces
- B64C9/323—Air braking surfaces associated with wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D5/00—Processes for applying liquids or other fluent materials to surfaces to obtain special surface effects, finishes or structures
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/02—Mounting or supporting thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/22—Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/32—Air braking surfaces
-
- C—CHEMISTRY; METALLURGY
- C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
- C09D—COATING COMPOSITIONS, e.g. PAINTS, VARNISHES OR LACQUERS; FILLING PASTES; CHEMICAL PAINT OR INK REMOVERS; INKS; CORRECTING FLUIDS; WOODSTAINS; PASTES OR SOLIDS FOR COLOURING OR PRINTING; USE OF MATERIALS THEREFOR
- C09D175/00—Coating compositions based on polyureas or polyurethanes; Coating compositions based on derivatives of such polymers
- C09D175/04—Polyurethanes
-
- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
- C08K3/00—Use of inorganic substances as compounding ingredients
- C08K3/18—Oxygen-containing compounds, e.g. metal carbonyls
- C08K3/20—Oxides; Hydroxides
- C08K3/22—Oxides; Hydroxides of metals
-
- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
- C08K3/00—Use of inorganic substances as compounding ingredients
- C08K3/34—Silicon-containing compounds
-
- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08L—COMPOSITIONS OF MACROMOLECULAR COMPOUNDS
- C08L23/00—Compositions of homopolymers or copolymers of unsaturated aliphatic hydrocarbons having only one carbon-to-carbon double bond; Compositions of derivatives of such polymers
- C08L23/02—Compositions of homopolymers or copolymers of unsaturated aliphatic hydrocarbons having only one carbon-to-carbon double bond; Compositions of derivatives of such polymers not modified by chemical after-treatment
- C08L23/04—Homopolymers or copolymers of ethene
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/25—Web or sheet containing structurally defined element or component and including a second component containing structurally defined particles
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Organic Chemistry (AREA)
- Materials Engineering (AREA)
- Wood Science & Technology (AREA)
- Life Sciences & Earth Sciences (AREA)
- Paints Or Removers (AREA)
- Laminated Bodies (AREA)
- Compositions Of Macromolecular Compounds (AREA)
- Road Signs Or Road Markings (AREA)
- Liquid Developers In Electrophotography (AREA)
- Developing Agents For Electrophotography (AREA)
- Lubricants (AREA)
Abstract
Disclosed is the use of a lacquer comprising a polyurethane matrix based on aliphatic components as well as fillers which are embedded in the polyurethane matrix and increase resistance to abrasion, as an abrasion-resistant coating of (a) aircraft landing flaps (2) in the contact zone with the spoilers (4), (b) in the abrasive zone of the cargo doors, or (c) in the abrasive zone of other aircraft components that mechanically produce friction on top of each other. Also disclosed are corresponding landing flaps and lacquers.
Description
Technical field
The present invention relates generally to the specific filler polyurethane paint that contains and is used for during operation the purposes of the wear-resistant coating in the appreciable wear zone of the aircraft components of mechanical friction mutually as wear-resistant coating, particularly conduct.
Background technology
Modern aircraft has the landing flap relevant with bumper/spoiler, and when when heading is observed, landing flap is arranged in the Background Region of wing, as shown in Figure 1.In the take-off and landing process, pack up or launch landing flap in order to adjust some aerodynamic performance.As shown in Figure 2, in this process, therefore the subregion of bumper/spoiler friction or wearing and tearing landing flap should must be protected in order to avoid damaged in the zone.
Current, the sheet steel that is called abrasion protection bar or abrasion protection metal sheet by application is protected the landing flap zone that has the wearing and tearing risk in airframe.Use abrasion protection bar (abrasion protection metal sheet) according to following order in the mode of effort:
Shelter landing flap (in the zone beyond the abrasion protection metal sheet) afterwards in part, clean the landing flap zone that to protect with solvent-laden purging medium.Utilize aquaseal (adhesives) that the abrasion protection metal sheet is applied on the landing flap then.Under vacuum, make the long relatively time (at least 12 hours) of sealant cures then.Carry out post-processing after the curing, specifically comprise and clean or remove masking steps.Be only then the landing flap japanning, abrasion protection metal sheet zone must masked and then be removed and be sheltered for this reason.
In the landing flap zone, use the abrasion protection bar to be specifically related to following shortcoming:
-use the abrasion protection metal sheet that generally has less thickness to cause before engaging and frequent crooked or scraping between joint aging time, and therefore cause high off gauge ratio.
-cleaning the landing flap zone that will protect and the completing steps that engages the abrasion protection metal sheet need highly accurate program.Even slightly depart from the needs that standard also can cause the adhesion errors of antifriction metal (AFM) plate and landing flap or cause not meeting visual design.
-before engaging, use the purging medium that contains solvent (containing VOC) to clean landing flap and abrasion protection bar, this is because only in this way just can realize essential surface quality.But, use solvent-laden purging medium to be considered to be day by day not expect.
-cleaning and engaging process are very consuming time.
Repair the part of-impaired abrasion protection metal sheet is impossible.Each reparation of impaired abrasion protection metal sheet relates to it is removed and again cleaning and engagement step from landing flap.
Therefore, the objective of the invention is to improve or eliminate in the above-mentioned shortcoming relevant at least some with use abrasion protection metal sheet (abrasion protection bar).
Summary of the invention
Special concern aircraft lands of the present invention wing flap with contact area bumper/spoiler in the zone.
According to first aspect, by using a kind of lacquer to realize above-mentioned purpose, this enamel-cover contains according to the present invention:
-based on the polyurethane matrix of aliphatic component; With
-embed in the polyurethane matrix and strengthen the filler of resistance to abrasion,
This lacquer as (a) aircraft lands wing flap with contact area bumper/spoiler in wear-resistant coating.
Unexpectedly, the polyurethane paint that comprises the filler that strengthens resistance to abrasion is suitable for replacing previously used abrasion protection metal sheet.
Used enamel-cover contains the polyurethane matrix based on aliphatic component, and it reveals slightly (human eye is sightless) variable color in thermal load (range of temperatures-55～100 ℃) down to multilist.In the embedding polyurethane matrix is the filler that strengthens resistance to abrasion.
For example paint or apply the lacquer system with still uncured state on the Topcoating outside at the outer bottom of landing flap by spraying or other in-situ solidifying method that is fit to.Dry layer thickness is usually in 10 μ m～300 mu m ranges.In order to realize＞bed thickness of 50 μ m, optional described coating procedure is repeated several times, up to the bed thickness that reaches hope.
Comprise based on the polyurethane matrix of aliphatic component and embed in the polyurethane matrix and the lacquer that strengthens the filler of resistance to abrasion not only be suitable for use as (a) aircraft lands wing flap with contact area bumper/spoiler in wear-resistant coating.Other possible use zone is: the eroded area of (b) cargo door for example, but described lacquer also can be advantageously used in (c) eroded area of other aircraft components of mechanical friction mutually during operation.Corresponding use is another theme of the present invention.
Another aspect of the present invention relate to the contact area of bumper/spoiler in have the aircraft lands wing flap of wear-resistant coating, wherein said coating is made up of the lacquer that solidifies, this enamel-cover contains or is composed of the following components:
-based on the polyurethane matrix of aliphatic component; With
-embed in the polyurethane matrix and strengthen the filler of resistance to abrasion.
In addition, the present invention relates to new wear resistant paint, this wear resistant paint is particularly suitable for applying the aircraft lands wing flap and contact area bumper/spoiler.
Unexpectedly, showing in the in-house research for a long time that lacquer used according to the invention (lacquer system) satisfies is relevant with the abrasion protection of landing flap, particularly from all requirements of machinery and visual aspects.In various requirement, following aspect is height correlation especially:
-with the binding power of base material
-resistance to abrasion
-chemical resistance good the opposing of water and hydraulic fluid (Skydrol) (particularly for)
-anti-jaundice property (heat and UV look solidity).In our research, only use based on the polyurethane matrix of aliphatic component and can realize high anti-UV; Use aromatic components to obtain the unsettled lacquer of UV.
And the advantage below producing:
-when particularly on the aircraft lands wing flap and contact area bumper/spoiler, using according to lacquer disclosed by the invention, can advantageously apply this lacquer by spraying coating process as fireproof paint (wear-resistant coating).Compare with the previously used method that applies the abrasion protection metal sheet, from time and cost viewpoint, this processing mode is obviously more favourable and destructive littler.This manufacturing process can automation.
-when use based on polyurethane according to of the present invention lacquer the time, eliminated and the relevant high off gauge ratio of use abrasion protection metal sheet.
-compare with using the abrasion protection metal sheet, exempted and sheltered and removed the step of sheltering.
-utilize the impaired wear-resistant coating according to purposes generation of the present invention of polyurethane paint system after the coating surface wearing and tearing, can locally to repair.
-before the use lacquer based on polyurethane according to the present invention comes wear-resistant coating, can use the purging medium that comprises the relatively small amount organic solvent to clean these parts (particularly landing flap).
-under-55 to+60 ℃ temperature, the use lacquer based on polyurethane with the embedding filler that strengthens resistance to abrasion according to the present invention obtains the good friction performance with the frictional fit member of being made by steel, CFRP (carbon fibre reiforced plastic) and titanium.
-to compare with using the abrasion protection metal sheet, weight significantly alleviates (when using on the passenger vehicle A340 type aircraft, alleviating about 10kg aloft).
Although a large amount of different fillers can embed in the polyurethane matrix to increase the resistance to abrasion of corresponding lacquer, some filler is very preferred.Therefore, it is particularly advantageous for example selecting filler from following filler:
Mohs (Mohs) hardness be at least 7 and particle diameter be 0.1 μ m＜d
50＜30 μ m, be preferably 2 μ m＜d
50The filler of＜15 μ m,
Mohs' scale of hardness be at most 2 and particle diameter be 3 μ m＜d
50The filler of＜50 μ m, and their compound.
Below, Mohs' scale of hardness is at least 7 filler and is called " firmly " filler, Mohs' scale of hardness is at most 2 filler and is called " soft " filler.
Unexpectedly, shown, used hard packing and wadding all to cause being used on significantly increasing so as the resistance to abrasion of the polyurethane paint of abrasion protection with respect to the landing flap of bumper/spoiler if meet particle size range disclosed herein.It is particularly advantageous using hard packing and wadding in polyurethane matrix simultaneously.
Hard packing is ceramic packing preferably; Wadding is the plastic material filler preferably.
Advantageously the inherent colour that not have especially or do not have to give prominence to as the material of filler itself promptly is a white material.But,, so also can use coloured or even the filler of black if the filler that the uses colourity of appreciable impact finished product lacquer just under high heap(ed) capacity is only promptly given color.In our research, shown that graphite (as the wadding material of black) has negative effect to the colourity of lacquer used according to the invention usually; Therefore lacquer used according to the invention does not preferably have graphite.
Ceramic packing is preferably selected from:
Carborundum, silicon dioxide, aluminium oxide, zirconia, akerite, boron nitride and their compound.
Wadding preferably is made up of ultra high molecular polyethylene, for example from the GUR 2126 of Ticona.
The preferred compound (having the above particle diameter that provides in all cases) that uses hard packing and wadding in lacquer used according to the invention, the weight ratio of filler is 1: 9～9: 1.When using the compound of hard packing and wadding, in our research, obtained good especially result.
In lacquer used according to the invention, the concentration of hard packing and wadding also is important to abrasion protection.Ratio with hard packing of above particle size range is preferably 5～35 weight %, more preferably 7～15 weight %, and/or the ratio with wadding of above particle size range is 5～35 weight %, preferred 7～15 weight %, more than all in the total weight of described lacquer.
As mentioned above, the invention still further relates to a kind of with the contact area of bumper/spoiler in have the aircraft lands wing flap of wear-resistant coating, wherein said coating is made up of the lacquer that solidifies, described enamel-cover contain based on the polyurethane matrix of aliphatic component and embed in the polyurethane matrix and strengthen resistance to abrasion filler or by based in the polyurethane matrix of aliphatic component and the embedding polyurethane matrix and the filler that strengthens resistance to abrasion form.
In this case, the coating of aircraft lands wing flap is preferably by forming such as above-mentioned preferred disclosed lacquer.
The invention still further relates to specific wear resistant paint, it is specially adapted to apply the aircraft lands wing flap and contact area bumper/spoiler, but it obviously also can be used for other purpose.Wear resistant paint according to the present invention comprises:
-based on the polyurethane matrix of aliphatic component and
-embed in the polyurethane matrix and strengthen the filler of resistance to abrasion,
Wherein said filler is selected from:
Mohs' scale of hardness be at least 7 and particle diameter be 0.01 μ m＜d
50The filler of＜30 μ m and
Above-mentioned filler and Mohs' scale of hardness be at most 2 and particle diameter be 3 μ m＜d
50The compound of the filler of＜50 μ m.
In this case, correspondingly, use above-mentioned filler according to the selection of filler material, weight ratio (for filler mixture) and concentration.
Except disclosed component (a) polyurethane matrix with (b) the selected filler, usually also comprise other component, particularly additive (surface additive, wetting additive, defoamer), pigment (coloring components according to lacquer of the present invention and lacquer used according to the invention; Because some pigment can be regarded as " filler " of the above-mentioned type under individual cases, therefore in this article, they are not other composition of lacquer but " filler ") and other optional component.
Description of drawings
Followingly by embodiment the present invention is described in more detail with reference to accompanying drawing, in these accompanying drawings:
Fig. 1 represents to have the aerocraft of the landing flap that applies the abrasion protection coating,
Fig. 2 represents to run through the cross sectional drawing of the wing section with the landing flap that applies the abrasion protection coating,
Fig. 3 represents to be used to study the wear testing platform of the resistance to abrasion of lacquer,
Fig. 4 a represents as according to the dynam of the pedestal of the wear testing platform of Fig. 3 and the schematic isometric of test geometry,
The lateral plan that Fig. 4 b presentation graphs 4a cuts,
Fig. 5 represents the figure of the particle diameter of hard packing for the influence of abrasional behavior,
The particle diameter that Fig. 6 represents wadding for the figure of the influence of abrasional behavior and
Fig. 7 represents the figure of packing density to the influence of resistance to abrasion.
The specific embodiment
Aerocraft 1 according to Fig. 1 has the landing flap 2 of packing up and launching in the take-off and landing process on its wing.
Fig. 2 with cross sectional drawing be illustrated in the landing flap 2 of bumper/spoiler 4 arranged beneath '.As shown in Figure 2, if bumper/spoiler 4 is not folded up bumper/spoiler 4 and landing flap 2 ' be in contact with one another so in friction area 6.If landing flap 2 ' for example launch for landing, so the bumper/spoiler in friction area 64 friction landing flaps 2 ', this means in this friction area 6 for landing flap 2 ' friction load.
Embodiment 1: according to the wear testing of PrEN 6124:
On the wear testing platform of special use, carry out wear testing, as far as possible accurately to simulate such as during operation will the occurring wear behavior on the aircraft lands wing flap according to PrEN 6124.
, the lacquer that detect is coated on the sample metal sheet (aluminium) for this reason, then described lacquer is fixed on the sample bench of friction testing platform with the sample metal sheet.
The sample metal sheet of japanning is corresponding to the protection by paints and lacquers zone of landing flap.Friction testing platform 10 according to PrEN 6124 shown in Figure 3.Friction testing platform 10 has three load containers 12 of filling tungsten powder, has the weight of G=566N separately.Load container 12 is fixed in the adjustable height and lockable first specimen holder 14 of linear guide bearings.In all cases, the weight of load container 12 is born a heavy burden second specimen holder 16 of linear guide bearings.The cooresponding frictional fit member of 16 clampings of second specimen holder and flow-disturbing wing flap, this frictional fit member is as the relative member (counter-member) that sample metal sheet 18 is born a heavy burden.Sample metal sheet 18 is arranged on the linear guide sample bench 20, and this linear guide sample bench 20 carries out the parallel motion of speed v=35mm/s, friction path s=80mm by hydraulic-driven 22.Carry out the SPS control of stress counter-rotating.Measure friction force by load unit 24, and determine coefficientoffriction by it.
The conditioning of sample metal sheet is following to be carried out:
The lacquer that will test is coated on the aluminium sheet and at room temperature deposited 7 days.On the wear testing platform, carry out wear testing according to PrEN 6124 then.
In each case, on the friction testing platform, move the friction path of 80mm according to PrEN 6124.Every cylinder is that the weight that each sample metal sheet loads is 566N.The speed of linear guide sample bench is 35mm/s.
The sample holder that to be made by the material that is usually used in the bumper/spoiler edge (for example, CFRP, titanium, steel 1.4548, polyamide, CuBe and silaatic) is on specimen holder.The size that sample sandwiches is 2 * 80mm.
In each case, apply 3.54N/mm painting of will testing
2Maximum load.
From Fig. 4 a and Fig. 4 b, obtain further details on the one hand, obtain the further details of arranging on the other hand about sample about dynam and test geometry.
Fig. 4 a represents the block diagram that basic sample is arranged.The specimen holder 16 that gravity G makes 16 heavy burdens of second specimen holder also therefore will comprise sample is pressed onto on the sample board metal 18.The sample board metal moves in the swing mode with the speed of the v=35mm/sec friction path s along 80mm.In this case, sample load is F=3.54N/mm
2
From according to the lateral plan of Fig. 4 b as can be seen, sample 26 is contained in second specimen holder 16, and gravity G is pressed on the sample board 18.Represent the sample 26 of flow-disturbing wing flap and the mating surfaces that specimen surface 18 has 2 * 80mm.In this case, sample 26 is bonded in the groove that the degree of depth is 0.5mm.
For according to the resistance to abrasion of PrEN 6124, correspondingly study the sample metal sheets that are coated with different lacquers, and after maximum 2000 circulations, determine wearing and tearing by the more different lacquer of test desk; The weight control of each sample is carried out once in per 250 circulations.
For more corresponding relative body (counter-body) (bumper/spoiler sample), make different bumper/spoiler materials stand maximum 2000 on-cycle loads; In this case, the weight control of body is relatively carried out once in per 250 circulations.
Under the situation that the bumper/spoiler sample is made by steel, titanium and CFRP (carbon fibre reiforced plastic), obtain coefficientoffriction≤0.6.
Probe temperature is adjusted to: 23 ℃ ,-55 ℃ and 60 ℃.
The tested media of using is: Skydrol and standard dirt (standard dirt).
Especially for wear testing, also must under the temperature of 60 ℃ and-55 ℃, implement.This is in order to guarantee that wear-resistant layer (when aerocraft is positioned at the hot-zone of the earth) in having the zone of high heat effect also is an actv..This is equally applicable to such as when landing or near the utmost point cool condition that occurs before landing.
By will be for this purpose the design-calculated sample study accordingly with refrigerant fluid or heating fluid rinsing.
We obtain a kind of like this result at own research according to PrEN 6124, promptly by embed the above-mentioned filler that strengthens resistance to abrasion in polyurethane matrix, can realize satisfying the superelevation resistance to abrasion of the high request in the aircraft industry.The filler that use has above-mentioned preferred feature has been proved to be particularly advantageous.
Should be noted that in this article that not only forming single-piece with filler has the resistance to abrasion that satisfies high request based on the lacquer of polyurethane, and also to be proved to be really on this degree such as some epoxy paint of commercial product Ceram Kote 54 be to be fit to fully; But lacquer not used according to the invention is nonconformity in having considered in the aircraft industry other test of carrying out about the needs that are fit to practical abrasion protection system, referring to following examples.
Embodiment 2: temperature test/hot yellow test:
Be coated in the lacquer system that to test on the 2024T3 type aluminium sheet commonly used in the airframe and at room temperature deposited 7 days.Measure each colourity as standard with colorimeter then.Then immediately under the temperature of 110 ℃ or 150 ℃, promptly such as in hot climate, under the temperature that may occur on the aircraft surface, depositing sample.After high temperature is deposited 100 hours, by comparing to determine colour difference with standard (starting value).
The colour space in the colour measurement is made up of value Da (red/green axle), Db (indigo plant/Huang axle) and DL (bright/dark axle).As the value of forming by three above-mentioned values, DE be described in colourity relatively in the similarity degree of two colourities.In this case, Db value and DE value are because the criterion that the colourity that UV light or thermal stress cause changes.In compare test, in Db value and DE value, all reflect the displacement of indigo plant/Huang axle, i.e. yellow.
In all cases, the lacquer based on polyurethane used according to the invention only has very slight colour difference.
In contrast, when using epoxy-resin systems Ceram Kote 54, produce very significantly chromaticity distortion, and be attended by unacceptable mechanical embrittlement corresponding to very strong jaundice.
Embodiment 3: the cross-cut according to DIN EN ISO 2409 is tested:
By testing the binding power of studying some lacquer according to the cross-cut of DIN EN ISO 2409.
At this, lacquer used according to the invention obviously has good especially performance.
Embodiment 4: filler material and particle diameter are to the influence of polishing machine:
4.1 hard packing
From having the aviation finish paint system based on polyurethane (based on aliphatic component) lacquer of high-wearing feature, produce the different particle diameters and the hard packing of different materials type.
Studied three kinds of different lacquers used according to the invention, (FS1, FS2, FS3) is as follows for its applied filler:
FS1: carborundum (Mohs' scale of hardness: 9.6); Particle diameter: d
50=1.5 μ m; Color: black, but only just colouration under very high addition.
Note, also other particle diameter and color have been carried out similar research.
FS2: aluminium oxide Al
2O
3(Mohs' scale of hardness: 9); Particle diameter: d
50=28 μ m; Color: white/ash.
Notice that also the particle diameter to other has carried out similar research.
FS3: pyrolytic silicon dioxide (SiO
2Nano particle) (Mohs' scale of hardness: 7); Particle diameter: d
50=12nm; Color: white.
Notice that also the particle diameter to other has carried out similar research.
In all cases, filler FS1, FS2 and FS3 all are being adjusted to 10 weight % as the concentration in the polyurethane aerocraft finish paint of matrix, in the total weight of lacquer.
Use titanium as relative member under study for action; Carry out wear testing according to PrEN 6124 usefulness test desks, referring to embodiment 1.
Fig. 5 illustrates the influence of particle diameter (and filler material).Cycle number is plotted on the abscissa and reaches 2000, and abrasion loss is plotted on the ordinate, and unit is mg, and reaches 140mg.Studied following coating:
K1: standard polyurethane aerocraft finish paint system;
K2: have 10% filler FS1 (d
50=1.5 μ m) standard polyurethane aerocraft finish paint system;
K3: have 10% filler FS2 (d
50Be about 28 μ m) standard polyurethane aerocraft finish paint system;
K4: have 10% filler FS3 (d
50=12nm) standard polyurethane aerocraft finish paint system.
As can be seen, compare with standard polyurethane aerocraft finish paint system, all polyurethane paints with filler all have the polishing machine of improvement or are cooresponding at least.The most compellent performance that is to use the K2 system of 10% filler FS1, this may mainly be because selected particle diameter.
Further research also shows, when the hard packing beyond the particle diameter that uses median value range 1.5～15 μ m, especially little and king-sized particle diameter (in interval according to the invention) often causes relatively poor result.
4.2 wadding
From having the aviation finish paint system based on polyurethane (based on aliphatic component) lacquer of high-wearing feature, produce the different particle diameters and the wadding of different materials type.
FS4: from the ultra-high molecular weight polyethylene poly-mer GUR 2126 of Ticona: according to our research, particle diameter d
50Be about 25～30 μ m; There is not d from maker
50Information; Color: milky; Form: pressed powder; Density: 0.93g.cm
3Bulk density: (DIN 53466) are 0.4kg/m at least
3Mohs' scale of hardness is about 2～2.5; Fusion temperature: DSC, 10K/ minute (ISO3146 method C): 130～135 ℃ (powder).
Filler FS4 is being adjusted to 5%, 10% or 15% as the concentration in the polyurethane aerocraft finish paint of matrix, in the total weight of lacquer.
Use titanium as relative member under study for action; Carry out wear testing according to PrEN 6124 usefulness test desks, referring to embodiment 1.
Fig. 6 illustrates the influence of particle diameter.Cycle number is plotted on the abscissa equally and reaches 2000, and abrasion loss is plotted on the ordinate equally, and unit is mg.Studied following coating:
K5: standard polyurethane aerocraft finish paint system;
K6: standard polyurethane aerocraft finish paint system with filler FS4 of 5%;
K7: standard polyurethane aerocraft finish paint system with filler FS4 of 10%;
K8: standard polyurethane aerocraft finish paint system with filler FS4 of 15%.
As can be seen, use the filler FS4 of all concentration all to realize the polishing machine of improving.When changing to 15% filler FS4 (becoming K8), be not further improved from K7 from 10% filler FS4.
In other research,, determined coefficientoffriction as the function of cycle number for aerocraft finish paint system K7.Even after 2000 circulations, coefficientoffriction is not higher than 0.33 yet.In contrast to this, for standard polyurethane aerocraft finish paint system K5 (not adding filler), only after 500 circulations coefficientoffriction just obviously greater than 0.4.
Embodiment 5: packing density is to the influence of resistance to abrasion:
The concentration of hard packing in the polyurethane paint matrix also influences the resistance to abrasion of finished product lacquer.
Fig. 7 is illustrated in the different amount of filler of use
Be the abrasion loss of unit with mg in the wear testing of Abraser 1000U, 1000g, Rolle CS 17.As amount of filler, following filler and amount of filler are added in the standard polyurethane aerocraft finish paint system.
Z1 does not add filler
Inorganic filler FS1 (the d of Z2 10%
50=1.5 μ m);
Inorganic filler FS1 (the d of Z3 20%
50=1.5 μ m);
Inorganic filler FS1 (the d of Z4 30%
50=1.5 μ m);
Inorganic filler FS2 (the d of Z5 10%
50=28 μ m);
Inorganic filler FS2 (the d of Z6 20%
50=28 μ m);
Inorganic filler FS2 (the d of Z7 30%
50=28 μ m);
Inorganic filler FS3 (the d of Z8 10%
50=12 μ m);
Inorganic filler FS3 (the d of Z9 20%
50=12 μ m).
As can be seen from Figure 7, when working concentration in polyurethane matrix is respectively the filler FS1 of 10 weight % or FS2, compare, obtain better wear resistance with corresponding lacquer with 20 weight % or 30 weight % fillers.In general, in a large amount of research, the concentration range of 7～15 weight % is proved to be particularly advantageous.
Claims (15)
1. the purposes of a lacquer, described enamel-cover contains:
-based on the polyurethane matrix of aliphatic component and
-embed in the described polyurethane matrix and strengthen the filler of resistance to abrasion,
Described lacquer is as (a) aircraft lands wing flap (2; 2 ') with the contact area of bumper/spoiler (4) in wear-resistant coating or (b) wear-resistant coating or (c) wear-resistant coating of the eroded area of other aircraft components of mechanical friction mutually during operation of the eroded area of cargo door.
2. according to the purposes of claim 1, wherein said filler is selected from:
Mohs' scale of hardness be at least 7 and particle diameter be 0.1 μ m＜d
50The filler of＜30 μ m,
Mohs' scale of hardness be at most 2 and particle diameter be 3 μ m＜d
50The filler of＜50 μ m,
With their compound.
3. according to the purposes of claim 2, wherein
Described Mohs' scale of hardness be at least 7 and particle diameter be 0.1 μ m＜d
50The filler of＜30 μ m is a ceramic packing,
And/or
Described Mohs' scale of hardness be at most 2 and particle diameter be 3 μ m＜d
50The filler of＜50 μ m is the plastic material filler.
4. according to the purposes of claim 3, wherein said ceramic packing is selected from:
Carborundum, silicon dioxide, aluminium oxide, zirconia, akerite and their compound.
5. according to each purposes in the claim 2～4, wherein use Mohs' scale of hardness be at least 7 and particle diameter be 0.1 μ m＜d
50The filler of＜30 μ m and Mohs' scale of hardness be at most 2 and particle diameter be 3 μ m＜d
50The compound of the filler of＜50 μ m,
The weight ratio of wherein said filler is 1: 9～9: 1.
6. according to each purposes in the claim 2～4, wherein
Mohs' scale of hardness be at least 7 and particle diameter be 0.1 μ m＜d
50The ratio of the filler of＜30 μ m is 5～35 weight %,
And/or
Mohs' scale of hardness be at most 2 and particle diameter be 3 μ m＜d
50The ratio of the filler of＜50 μ m is 5～35 weight %,
In each case all in the total weight of described lacquer.
7. according to the purposes of claim 6, wherein
Mohs' scale of hardness be at least 7 and particle diameter be 0.1 μ m＜d
50The ratio of the filler of＜30 μ m is 7～15 weight %,
And/or
Mohs' scale of hardness be at most 2 and particle diameter be 3 μ m＜d
50The ratio of the filler of＜50 μ m is 7～15 weight %,
In each case all in the total weight of described lacquer.
One kind with the contact area of bumper/spoiler (4) in have the aircraft lands wing flap (2 of wear-resistant coating; 2 '), wherein said coating is made up of the lacquer that solidifies, and described enamel-cover contains or is composed of the following components:
-based on the polyurethane matrix of aliphatic component and
-embed in the polyurethane matrix and strengthen the filler of resistance to abrasion.
9. aircraft lands wing flap (2 according to Claim 8; 2 '), wherein use according to each lacquer in the claim 1～6.
10. one kind is used to apply aircraft lands wing flap (2; 2 ') with the wear resistant paint of the contact area of bumper/spoiler (4), described enamel-cover contains:
-based on the polyurethane matrix of aliphatic component and
-embed in the polyurethane matrix and strengthen the filler of resistance to abrasion,
Wherein said filler is selected from:
Mohs' scale of hardness be at least 7 and particle diameter be 0.1 μ m＜d
50The filler of＜30 μ m and
Above-mentioned filler and Mohs' scale of hardness be at most 2 and particle diameter be 3 μ m＜d
50The compound of the filler of＜50 μ m.
11. according to the wear resistant paint of claim 10, wherein
Described Mohs' scale of hardness be at least 7 and particle diameter be 0.1 μ m＜d
50The filler of＜30 μ m is a ceramic packing,
And/or
Described Mohs' scale of hardness be at most 2 and particle diameter be 3 μ m＜d
50The filler of＜50 μ m is the plastic material filler.
12. according to the wear resistant paint of claim 11, wherein said ceramic packing is selected from:
Carborundum, silicon dioxide, aluminium oxide, zirconia, akerite, boron nitride and their compound.
13. according to each the wear resistant paint in the claim 10～12, wherein use Mohs' scale of hardness be at least 7 and particle diameter be 0.1 μ m＜d
50The filler of＜30 μ m and Mohs' scale of hardness be at most 2 and particle diameter be 3 μ m＜d
50The compound of the filler of＜50 μ m,
The weight ratio of described filler is 1: 9～9: 1.
14. according to each the wear resistant paint in the claim 10～12, wherein
Mohs' scale of hardness be at least 7 and particle diameter be 0.1 μ m＜d
50The ratio of the filler of＜30 μ m is 5～35 weight %,
And/or
Mohs' scale of hardness be at most 2 and particle diameter be 3 μ m＜d
50The ratio of the filler of＜50 μ m is 5～35 weight %,
In each case all in the total weight of described lacquer.
15. according to the wear resistant paint of claim 14, wherein
Mohs' scale of hardness be at least 7 and particle diameter be 0.1 μ m＜d
50The ratio of the filler of＜30 μ m is 7～15 weight %,
And/or
Mohs' scale of hardness be at most 2 and particle diameter be 3 μ m＜d
50The ratio of the filler of＜50 μ m is 7～15 weight %,
In each case all in the total weight of described lacquer.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102005048434A DE102005048434A1 (en) | 2005-10-07 | 2005-10-07 | Polyurethane coatings as scuff protection coatings |
| DE102005048434.4 | 2005-10-07 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101277869A CN101277869A (en) | 2008-10-01 |
| CN100579866C true CN100579866C (en) | 2010-01-13 |
Family
ID=37622090
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200680036844A Expired - Fee Related CN100579866C (en) | 2005-10-07 | 2006-09-27 | Polyurethane lacquers as abrasion-resistant coatings |
Country Status (10)
| Country | Link |
|---|---|
| US (1) | US9694901B2 (en) |
| EP (1) | EP1931565B1 (en) |
| JP (1) | JP2009511314A (en) |
| CN (1) | CN100579866C (en) |
| AT (1) | ATE500131T1 (en) |
| BR (1) | BRPI0617153A2 (en) |
| CA (1) | CA2624489C (en) |
| DE (2) | DE102005048434A1 (en) |
| RU (1) | RU2457150C2 (en) |
| WO (1) | WO2007042398A1 (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DK2655460T3 (en) * | 2010-12-20 | 2015-06-22 | Klebchemie M G Becker Gmbh | Reactive polyurethane composition with abrasion resistant fillers |
| CN103466078A (en) * | 2013-08-23 | 2013-12-25 | 中国航空工业集团公司西安飞机设计研究所 | Detachable integral slat trailing edge structure |
| CN106280401A (en) * | 2016-09-19 | 2017-01-04 | 南京工程学院 | Multiple dimensioned SiC particulate hybrid buildup compound polyurethane material and preparation method thereof |
| WO2019097791A1 (en) * | 2017-11-14 | 2019-05-23 | 株式会社豊田自動織機 | Sliding member and method for manufacturing same |
| CN114394258B (en) * | 2022-01-18 | 2024-07-30 | 湖南航天环宇通信科技股份有限公司 | Mechanical property experimental device and method for aileron driving mechanism |
| CN114854295B (en) * | 2022-04-14 | 2024-08-13 | 山西维力固科技股份有限公司 | Polyurethane-based wear-resistant composite material and construction process |
Family Cites Families (25)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US398997A (en) * | 1889-03-05 | Dust-pan | ||
| SU513065A1 (en) * | 1974-04-05 | 1976-05-05 | Предприятие П/Я Р-6875 | Coating composition |
| US3986997A (en) | 1974-06-25 | 1976-10-19 | Dow Corning Corporation | Pigment-free coating compositions |
| DE2556203A1 (en) * | 1975-12-13 | 1977-06-23 | Heinz Hoelter | Coatings for building elements - of improved fire-, abrasion-, corrosion-and oil-resistance, contain silica flour and/or ferrosilicon oxide dust |
| SU659298A1 (en) * | 1977-03-25 | 1979-04-30 | Предприятие П/Я А-1977 | Apparatus for metering-out blanks by volume |
| US4225372A (en) * | 1979-01-25 | 1980-09-30 | The United States Of America As Represented By The National Aeronautics And Space Administration | Surface finishing |
| DE3527497A1 (en) | 1985-07-31 | 1987-02-12 | Airbus Gmbh | WING WITH EXTENDABLE FLAP AND CHANGEABLE BURNER |
| US5221337A (en) * | 1990-02-14 | 1993-06-22 | W. R. Grace & Co.-Conn. | SiO2 flatting agent, process for its production and its use |
| DE4304491A1 (en) | 1993-02-15 | 1994-08-18 | Zeller & Gmelin Gmbh & Co | Use of hard fillers in radiation-curable lacquers, coatings and printing inks in order to increase the abrasion resistance |
| US5845877A (en) | 1993-06-10 | 1998-12-08 | Lockheed Martin Corporation | Sealing assembly for reducing gaps between movable control surfaces of an aircraft |
| DE4406443A1 (en) * | 1994-02-28 | 1995-08-31 | Huels Chemische Werke Ag | Process for the preparation of blocked polyisocyanates and their use in polyurethane coating systems |
| DE19529987A1 (en) * | 1995-08-07 | 1997-02-13 | Kunnemeyer Hornitex | Prodn. of highly abrasion resistant lacquer coatings - with wear-reducing agent, pref. metal oxide, applied before or after the lacquer |
| JP3898256B2 (en) * | 1996-08-28 | 2007-03-28 | 大日本印刷株式会社 | Decorative sheet |
| US5977269A (en) | 1997-10-30 | 1999-11-02 | Foster-Miller, Inc. | Polyester/vinyl dioxolane based coating compositions |
| US6300457B1 (en) * | 1996-09-23 | 2001-10-09 | Foster Miller, Inc. | Polyester/polyurethane vinyl dioxolane based coating compositions |
| EP0853095A1 (en) * | 1997-01-10 | 1998-07-15 | Alcan International Limited | Abrasion resistant polymer |
| US6291078B1 (en) * | 1997-10-22 | 2001-09-18 | Mannington Mills, Inc. | Surface coverings containing aluminum oxide |
| GB2323576B (en) | 1997-03-26 | 2001-08-22 | British Aerospace | Fairing arrangements for aircraft |
| US7854967B2 (en) * | 1998-09-11 | 2010-12-21 | The Boeing Company | Method for pre-sealing faying surfaces of components and faying surfaces pre-sealed thereby |
| CN1315956C (en) * | 1999-03-03 | 2007-05-16 | 瓦尔斯帕供应公司 | Abrasion resistant coatings |
| EP1268568A4 (en) * | 2000-02-15 | 2003-05-28 | Foster Miller Inc | No voc radiation curable resin compositions |
| US20020137872A1 (en) * | 2000-12-08 | 2002-09-26 | Schneider John R. | Coating compositions providing improved mar and scratch resistance and methods of using the same |
| US20030017797A1 (en) * | 2001-03-28 | 2003-01-23 | Kendall Philip E. | Dual cured abrasive articles |
| US6878771B2 (en) * | 2002-09-30 | 2005-04-12 | Bhaskar R. Urs | Matte-finish polyurethane coating composition |
| US7323248B2 (en) * | 2004-03-13 | 2008-01-29 | Ecology Coatings, Inc. | Environmentally friendly coating compositions for coating composites, coated composites therefrom, and methods, processes and assemblages for coating thereof |
-
2005
- 2005-10-07 DE DE102005048434A patent/DE102005048434A1/en not_active Ceased
-
2006
- 2006-09-27 RU RU2008118141/11A patent/RU2457150C2/en not_active IP Right Cessation
- 2006-09-27 DE DE502006009019T patent/DE502006009019D1/en active Active
- 2006-09-27 US US12/089,158 patent/US9694901B2/en active Active
- 2006-09-27 BR BRPI0617153-2A patent/BRPI0617153A2/en not_active IP Right Cessation
- 2006-09-27 AT AT06806849T patent/ATE500131T1/en active
- 2006-09-27 WO PCT/EP2006/066796 patent/WO2007042398A1/en active Application Filing
- 2006-09-27 CN CN200680036844A patent/CN100579866C/en not_active Expired - Fee Related
- 2006-09-27 CA CA2624489A patent/CA2624489C/en not_active Expired - Fee Related
- 2006-09-27 JP JP2008533977A patent/JP2009511314A/en active Pending
- 2006-09-27 EP EP06806849A patent/EP1931565B1/en not_active Not-in-force
Also Published As
| Publication number | Publication date |
|---|---|
| EP1931565B1 (en) | 2011-03-02 |
| CA2624489A1 (en) | 2007-04-19 |
| EP1931565A1 (en) | 2008-06-18 |
| RU2008118141A (en) | 2009-11-20 |
| DE102005048434A1 (en) | 2007-04-26 |
| JP2009511314A (en) | 2009-03-19 |
| RU2457150C2 (en) | 2012-07-27 |
| CN101277869A (en) | 2008-10-01 |
| ATE500131T1 (en) | 2011-03-15 |
| DE502006009019D1 (en) | 2011-04-14 |
| CA2624489C (en) | 2013-04-09 |
| US20090075058A1 (en) | 2009-03-19 |
| US9694901B2 (en) | 2017-07-04 |
| WO2007042398A1 (en) | 2007-04-19 |
| BRPI0617153A2 (en) | 2011-07-12 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN100579866C (en) | Polyurethane lacquers as abrasion-resistant coatings | |
| CA2576746C (en) | Exterior paint formulation | |
| DK2616230T3 (en) | Method and System for Manufacturing a Moisture Resistant Thin Layer Fiber Composite Material | |
| Salvant et al. | Nanoindentation and the micromechanics of Van Gogh oil paints | |
| CN110352132A (en) | Cosmetic sheet and decorative panel | |
| US8415005B2 (en) | Non-stick coating | |
| Zouari et al. | Scratch resistance and tribological performance of thermosetting composite powder coatings system: A comparative evaluation | |
| CA2830807A1 (en) | Wheelsets for trackbound vehicles or parts of these and coating process | |
| EP0106707A1 (en) | Coating composition | |
| Liscano et al. | Correlation between microstructural characteristics and the abrasion wear resistance of sealed thermal-sprayed coatings | |
| Ayrilmis | Surface properties of oriented strand board coated by electrostatic dry powder spray deposition technique | |
| CN110616024A (en) | Wear-resistant floor coating and construction method thereof | |
| Attar | Hardness evaluation of thin ceramic coatings on tool steel | |
| Tang et al. | Quantitative measurement of adhesion between polypropylene blends and paints by tensile mechanical testing | |
| CN106810923A (en) | A kind of car paint of easy cleaning and preparation method thereof | |
| Ramezanzadeh et al. | The effect of basecoat pigmentation on the scratch resistance and weathering performance of an acrylic–melamine basecoat/clearcoat automotive finish | |
| Wang et al. | Evaluation of thermally-sprayed ceramic coatings using a novel ball-on-inclined plane scratch method | |
| Padenko et al. | Tribology of innovative polybenzimidazole (PBI) coatings | |
| Lang et al. | Characterization of nanostructured coatings based on oxides for tribological applications | |
| JP2007054766A (en) | Brilliant feeling coating for repair and method for repairing of brilliant feeling coating film using the same | |
| EP2260161A1 (en) | Coated wooden floor panel | |
| Belov et al. | Development of a scratch test method to determine adhesion and strength properties of coated steel sheets | |
| Rogers | Architectural Coatings | |
| Delucchi et al. | Influence of thickness on mechanical properties and crack-bridging ability of coatings for concrete | |
| Kodumuri et al. | Federal Highway Administration 100-year coating study. |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C56 | Change in the name or address of the patentee | ||
| CP01 | Change in the name or title of a patent holder |
Address after: hamburg Patentee after: Airbus GmbH Address before: hamburg Patentee before: Airbus GmbH |
|
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20100113 Termination date: 20200927 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |